EP2886206B1 - Procédé de revêtement d'une douille - Google Patents

Procédé de revêtement d'une douille Download PDF

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Publication number
EP2886206B1
EP2886206B1 EP13400041.3A EP13400041A EP2886206B1 EP 2886206 B1 EP2886206 B1 EP 2886206B1 EP 13400041 A EP13400041 A EP 13400041A EP 2886206 B1 EP2886206 B1 EP 2886206B1
Authority
EP
European Patent Office
Prior art keywords
cylindrical
bushing
cylindrical bushing
liner
radius
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13400041.3A
Other languages
German (de)
English (en)
Other versions
EP2886206A1 (fr
Inventor
Roberto Gusmini
Thomas Schmitz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters Deutschland GmbH
Original Assignee
Airbus Helicopters Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Helicopters Deutschland GmbH filed Critical Airbus Helicopters Deutschland GmbH
Priority to EP13400041.3A priority Critical patent/EP2886206B1/fr
Publication of EP2886206A1 publication Critical patent/EP2886206A1/fr
Application granted granted Critical
Publication of EP2886206B1 publication Critical patent/EP2886206B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
    • B05D5/08—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain an anti-friction or anti-adhesive surface
    • B05D5/083—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain an anti-friction or anti-adhesive surface involving the use of fluoropolymers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
    • B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
    • B05D3/0254—After-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/20—Sliding surface consisting mainly of plastics
    • F16C33/208—Methods of manufacture, e.g. shaping, applying coatings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D2506/00—Halogenated polymers
    • B05D2506/10—Fluorinated polymers
    • B05D2506/15—Polytetrafluoroethylene [PTFE]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2326/00—Articles relating to transporting
    • F16C2326/43—Aeroplanes; Helicopters

Definitions

  • the invention relates to a method of coating a bushing and more particularly to a method of coating a bushing of a main rotor blade of a helicopter with the features of the preamble of claim 1.
  • the rotor blades of a helicopter are attached to a steel made rotor mast by means of integrated bearing bushes made of steel and mounted by titan made fit bolts.
  • the close contact of steel to steel and/or steel to titan causes contact corrosion due to micro movements in the contact area of an outer surface of the steel bushes with the steel attachment to the main rotor shaft and the associated cracks which occur in the area of rotor attachment.
  • the document JP2009103194 describes a production method of a cylindrical back plate with a multi-layered sliding member exhibiting friction/abrasion characteristics at high loading usage and at usage under a dry friction condition.
  • the multi-layered sliding member is bonded to the inner surface of the cylindrical back plate by a press-fitting process using a metal pipe having a large thermal expansion.
  • the solution is provided with a method of coating a bushing and more particularly with a method of coating a bushing of a main rotor blade of a helicopter with the features of claim 1.
  • a method of coating a cylindrical bushing and more particularly a method of coating a cylindrical bushing of a main rotor blade of a helicopter comprises the steps of providing a cylindrical bushing with a cylindrical inner surface side with an inner radius r ri and a cylindrical outer surface side with an outer radius r ro and further providing an essentially cylindrical inner liner comprising polytetrafluoroethylene (PTFE), said inner liner having an outer radius r lo ⁇ r ri and an inner radius r li .
  • PTFE polytetrafluoroethylene
  • the bonding agent is applied to the inner liner with PTFE and the inner liner is attached manually by means of the bonding agent to the cylindrical inner surface side of the cylindrical bushing.
  • an essentially cylindrical outer liner comprising PTFE is provided, said outer liner having an outer radius roo and an inner radius r oi ⁇ r ro .
  • a carbon fibre reinforced plastic (CFRP)-ring with an inner radius r ci ⁇ r oo and a coefficient of thermal expansion lower than the coefficient of thermal expansion of the cylindrical bushing and still further provided is a housing. Bonding agent is applied to the outer liner with PTFE.
  • the outer liner is manually attached by means of the bonding agent on the cylindrical outer surface side of the cylindrical bushing and the CRFP-ring is positioned on the outer liner on the cylindrical outer surface side of the cylindrical bushing.
  • the cylindrical bushing is positioned with the installed CFRP ring in the housing and the metallic pin is installed inside the inner liner on the cylindrical inner surface side of the cylindrical bushing and in the housing.
  • the cylindrical bushing is heated with the installed CFRP ring and the metallic pin in the housing at approx. 135°C during 90 min.. Due to the different thermal expansion coefficients of the cylindrical bushing, the CFRP ring and the metallic pin, both PTFE-liners are evenly pressed against the bushing when the assembly is heated.
  • the cylindrical bushing with the installed CFRP ring and the metallic pin is cooled at room temperature during 30. min..
  • the bonded cylindrical bushing with the installed CFRP ring and the metallic pin are removed from the housing, the cylindrical bushing is separated from the CFRP ring and the metallic pin and the cylindrical bushing is cleaned.
  • Bearing bushes made according to the method of the invention with coated inner and outer surfaces avoid any direct contact of titan bolts to e. g. steel bushings and from the steel bushings with a steel rotor hub and thus avoid contact corrosion.
  • the inventive method allows the manufacturing of a cylindrical bushing equipped with liners comprising PTFE on both, the outer and the inner surface sides.
  • a main advantage of the inventive method is the high quality of the liner application process.
  • a cylindrical bushing and more particularly a cylindrical bushing of a main rotor blade of a helicopter is provided with a cylindrical inner surface side with an inner radius and a cylindrical outer surface side with an outer radius, said cylindrical inner surface side and the cylindrical outer surface side being each coated with essentially cylindrical liners comprising PTFE according to the inventive method.
  • cylindrical bushing is provided with a flange.
  • the liners comprise PTFE as a thin sheet of glass fibre reinforced PTFE-mesh.
  • the PTFE-liner may be only on the outer diameter of the bushing.
  • a method for manufacturing a cylindrical bushing 1 for the attachment of main rotor blades (see Fig. 4 ) to a main rotor shaft (not shown) of a helicopter comprises in a first step the provision of a tooling with a housing 2, a CRFP-ring 3 and an aluminium pin 4. Further provided are a bonding agent (not shown) and an inner liner 5 and an outer liner 6, respectively made of a thin sheet of glass fibre reinforced PTFE-mesh.
  • the housing 2 is essentially cylindrical with a stepped central opening 7 surrounded by an annular planar contact surface 8 perpendicular to the stepped central opening 7. Radial inside the contact surface 8 a lower flange 9 is provided with a planar surface perpendicular to the stepped central opening 7.
  • the cylindrical bushing 1 has a cylindrical inner surface side with an inner radius r ri , a cylindrical outer surface side with an outer radius r ro and a flange 10 projecting radially outward from an upper end of the cylindrical bushing 1.
  • the flange 10 extends perpendicularly to a central axis 11 (see Fig. 2 ) of the cylindrical bushing 1.
  • the flange 10 is coaxial to said central axis 11.
  • the cylindrical inner liner 5 has an outer radius r lo ⁇ r ri and an inner radius r li .
  • the outer liner 6 has an outer radius r oo and an inner radius r oi ⁇ r ro .
  • the aluminium pin 4 has an upper section 13 with a radius > than its middle section radius r p and the aluminium pin 4 has a lower section 14 with a radius ⁇ than its middle section radius rp.
  • the CFRP-ring 3 has a lower bearing surface 15 for abutment against the lower flange 9 of the housing 2 and the CFRP-ring 3 has an upper bearing surface 16 for abutment from below against the flange 10 of the cylindrical bushing 1.
  • the cylindrical inner surface side of the cylindrical bushing 1 is coated with the inner liner 5.
  • the cylindrical outer surface side of the cylindrical bushing 1 is coated with the outer liner 6.
  • the CRFP ring 3 is positioned coaxially with the outer liner 6 on the cylindrical outer surface side of the cylindrical bushing 1.
  • a third step the cylindrical bushing 1 with the CRFP ring 3 on the outer liner 6 is inserted coaxially into the stepped central opening 7 of the housing 2.
  • the lower bearing surface 15 of the CFRP-ring 3 is supported by the lower flange 9 of the housing 2.
  • the aluminium pin 4 is inserted coaxially into the inner liner 5 on the cylindrical inner surface side of the cylindrical bushing 1 and into the stepped central opening 7 of the housing 2 till the upper section 13 of the aluminium pin 4 abuts from above against the flange 10 of the cylindrical bushing 1.
  • Fig. 2 , 3 corresponding features are referred to with the references of Fig. 1 .
  • the aluminium pin 4 is inserted coaxially with its middle section 12 and its lower section 14 into the stepped central opening 7 of the housing 2 whereby the lower section 14 fits with low tolerances into the lowest part of the stepped central opening 7 of the housing 2 allowing to manufacture a bushing with a concentricity of the inner liner 5 and/or outer liner 6 of 0,02 mm to 0,05 mm relative to a center axis of the bushing.
  • the cylindrical steel bushing 1 with the inner and the outer liners 5, 6 and the CRFP ring 3 with the CRFP ring 3 between the outer liner 6 on the cylindrical steel bushing 1 and the housing 2.
  • the flange 10 of the cylindrical steel bushing 1 is supported by the planar contact surface 8 of the housing 2 for exact angular positioning of the cylindrical steel bushing 1 relative to the housing 2 with an angular tolerance of the upper bushing flange to the center axis of the bushing up to 0,02 mm - 0,05 mm.
  • the lower bearing surface 15 of the CFRP-ring 3 is supported by the lower flange 9 in the stepped central opening 7.
  • the upper section 13 of the aluminium pin 4 is supported by the flange 10 of the cylindrical steel bushing 1.
  • the CRFP ring 3 is provided on its inner radius with an inner step 17 for exact longitudinal positioning of the inner liner 5 and/or outer liner 6 with tolerances of up to 0,05 to 0,1 mm.
  • the lower flange 9 of the housing 2 is provided with a flange nose 18 for exact longitudinal positioning of the inner liner 5 and/or outer liner 6 with tolerances of up to 0,05 to 0,1 mm.
  • two cylindrical bushings 1 are mounted coaxial to a titanium blade attachment bolt 21 with a bolt head 22 for the attachment of a main rotor blade 20 to the main rotor shaft (not shown) of the helicopter.
  • An upper one of the two cylindrical bushings 1 coaxially holds an upper mast flange 23 made of steel to the titanium blade attachment bolt 21.
  • the main rotor blade 20 is in contact with the flange 10 of the upper one of the two cylindrical bushings 1.
  • a lower one of the two cylindrical bushings 1 is coaxially mounted between a lower mast flange 24 made of steel and the titanium blade attachment bolt 21 and the main rotor blade 20 is again in contact with the flange 10 of the lower one of the two cylindrical bushings 1.
  • a blade attachment bolt nut 25 fixes the two cylindrical bushings 1, the upper and lower mast flanges 23, 24 and the main rotor blade 20 to the titanium blade attachment bolt 21.
  • Outer liners 6 made of a thin sheet of glass fibre reinforced PTFE-mesh are provided on the two cylindrical steel bushings 1 coaxially to the titanium blade attachment bolt 21 and in contact with the upper and lower mast flanges 23, 24.
  • Inner liners 5 made of a thin sheet of glass fibre reinforced PTFE-mesh are provided on the two cylindrical steel bushings 1 coaxially to and in contact with the titanium blade attachment bolt 21.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Sliding-Contact Bearings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (2)

  1. Méthode de revêtement d'un palier cylindrique (1) comprenant les étapes suivantes :
    - Produire un palier cylindrique (1) avec une face intérieure cylindrique de rayon intérieur rri et une face extérieure cylindrique de rayon extérieur rro,
    - Produire une garniture intérieure (5) cylindrique en polytétrafluoroéthylène (PTFE), ladite garniture intérieure (5) ayant un rayon extérieur rlo ≤ rri et un rayon intérieur rli,
    - Produire un adhésif et une broche métallique (4) de rayon extérieur rpo ≤ rli et dont le coefficient de dilatation thermique est supérieur au coefficient de dilatation thermique du palier cylindrique (1),
    - Appliquer l'adhésif sur la garniture intérieure (5) avec du PTFE, et
    - fixer manuellement la garniture intérieure (5) au moyen de l'adhésif à la face intérieure cylindrique du palier cylindrique (1),
    Caractérisée par
    - Produire une garniture extérieure (6) cylindrique en PTFE, ladite garniture extérieure (6) ayant un rayon extérieur roo et un rayon intérieur roi ≤ rro,
    - Produire un anneau en plastique renforcé de fibres de carbone (3) de rayon intérieur rci ≤ roo et dont le coefficient de dilatation thermique est inférieur au coefficient de dilatation thermique du palier cylindrique (1),
    - Produire un logement (2),
    - Appliquer un adhésif sur la garniture extérieure (6), et
    - Fixer manuellement la garniture extérieure (6) au moyen de l'adhésif à la face extérieure cylindrique du palier cylindrique (1),
    - Positionner l'anneau en plastique renforcé de fibres de carbone (3) sur la garniture extérieure (6) sur la face extérieure cylindrique du palier cylindrique (1)
    - Positionner le palier cylindrique (1) avec l'anneau en plastique renforcé de fibres de carbone (3) installé dans le logement (2),
    - Installer la broche métallique (4) à l'intérieur de la garniture intérieure (5) sur la face intérieure cylindrique du palier cylindrique (1) et dans le logement (2),
    - Chauffer le palier cylindrique (1) avec l'anneau en plastique renforcé de fibres de carbone (3) installé et la broche métallique (4) dans le logement (2) à 135 °C pendant 90 minutes environ, et
    - Refroidir le palier cylindrique (1) avec l'anneau en plastique renforcé de fibres de carbone (3) installé et la broche métallique (4) à température ambiante pendant 30 minutes et
    - Retirer le palier cylindrique (1) collé avec l'anneau en plastique renforcé de fibres de carbone (3) installé et la broche métallique (4) depuis le logement (2),
    - Libérer le palier cylindrique (1) de l'anneau en plastique renforcé de fibres de carbone (3) et la broche métallique (4) et nettoyer le palier cylindrique (1).
  2. Méthode de la revendication 1, dans laquelle le palier cylindrique (1) est destiné à un rotor principal d'hélicoptère.
EP13400041.3A 2013-12-19 2013-12-19 Procédé de revêtement d'une douille Active EP2886206B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13400041.3A EP2886206B1 (fr) 2013-12-19 2013-12-19 Procédé de revêtement d'une douille

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13400041.3A EP2886206B1 (fr) 2013-12-19 2013-12-19 Procédé de revêtement d'une douille

Publications (2)

Publication Number Publication Date
EP2886206A1 EP2886206A1 (fr) 2015-06-24
EP2886206B1 true EP2886206B1 (fr) 2016-05-18

Family

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EP13400041.3A Active EP2886206B1 (fr) 2013-12-19 2013-12-19 Procédé de revêtement d'une douille

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113426645A (zh) * 2021-08-30 2021-09-24 天津飞旋科技股份有限公司 旋转烘焙监控系统、方法、装置及计算机可读存储介质

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10183388B2 (en) 2016-08-01 2019-01-22 Sikorsky Aircraft Corporation Cuff-blade attachment bushing removal

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6264369B1 (en) * 1999-01-29 2001-07-24 General Electric Company Variable vane seal and washer materials
JP2004144232A (ja) * 2002-10-25 2004-05-20 Daido Metal Co Ltd 軸受の内面の加工方法
GB2414425A (en) * 2004-05-28 2005-11-30 Railko Ltd Surface coating for a composite coating

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113426645A (zh) * 2021-08-30 2021-09-24 天津飞旋科技股份有限公司 旋转烘焙监控系统、方法、装置及计算机可读存储介质
CN113426645B (zh) * 2021-08-30 2021-11-09 天津飞旋科技股份有限公司 旋转烘焙监控系统、方法、装置及计算机可读存储介质

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